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GOE 501 AIRFOIL (goe501-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 501 AIRFOIL (goe501-il)
Reynolds number: 500,000
Max Cl/Cd: 113.25 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe501-il-500000.txt
Download as CSV file: xf-goe501-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 501 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1215   0.10040   0.09790  -0.0897   0.9758   0.0421
 -10.500  -0.3536   0.02910   0.02557  -0.1677   0.9430   0.0391
 -10.250  -0.3407   0.02663   0.02270  -0.1699   0.9341   0.0399
 -10.000  -0.3235   0.02410   0.01994  -0.1713   0.9275   0.0408
  -9.750  -0.2989   0.02352   0.01934  -0.1715   0.9225   0.0415
  -9.500  -0.2759   0.02306   0.01884  -0.1712   0.9155   0.0424
  -9.250  -0.2500   0.02241   0.01810  -0.1715   0.9106   0.0434
  -9.000  -0.2277   0.02131   0.01680  -0.1716   0.9039   0.0444
  -8.750  -0.2038   0.02025   0.01550  -0.1718   0.8972   0.0455
  -8.500  -0.1789   0.01905   0.01403  -0.1722   0.8914   0.0465
  -8.250  -0.1555   0.01805   0.01300  -0.1720   0.8833   0.0476
  -8.000  -0.1281   0.01750   0.01236  -0.1721   0.8776   0.0485
  -7.750  -0.1026   0.01697   0.01175  -0.1720   0.8701   0.0496
  -7.500  -0.0757   0.01641   0.01107  -0.1720   0.8641   0.0508
  -7.250  -0.0482   0.01595   0.01045  -0.1721   0.8584   0.0521
  -7.000  -0.0213   0.01560   0.00996  -0.1719   0.8517   0.0530
  -6.750   0.0050   0.01445   0.00868  -0.1721   0.8463   0.0544
  -6.500   0.0319   0.01397   0.00818  -0.1721   0.8406   0.0557
  -6.250   0.0592   0.01364   0.00781  -0.1720   0.8345   0.0571
  -6.000   0.0875   0.01334   0.00740  -0.1721   0.8295   0.0588
  -5.750   0.1150   0.01304   0.00702  -0.1720   0.8241   0.0603
  -5.500   0.1428   0.01282   0.00672  -0.1719   0.8186   0.0613
  -5.250   0.1700   0.01203   0.00585  -0.1720   0.8134   0.0634
  -5.000   0.1974   0.01171   0.00552  -0.1719   0.8083   0.0653
  -4.750   0.2252   0.01147   0.00526  -0.1719   0.8032   0.0675
  -4.500   0.2535   0.01125   0.00497  -0.1719   0.7987   0.0695
  -4.250   0.2821   0.01111   0.00474  -0.1719   0.7943   0.0710
  -4.000   0.3092   0.01060   0.00423  -0.1719   0.7895   0.0739
  -3.750   0.3371   0.01035   0.00397  -0.1719   0.7849   0.0769
  -3.500   0.3658   0.01018   0.00374  -0.1719   0.7804   0.0799
  -3.250   0.3939   0.01005   0.00357  -0.1719   0.7758   0.0821
  -3.000   0.4217   0.00976   0.00329  -0.1718   0.7709   0.0870
  -2.750   0.4500   0.00960   0.00310  -0.1718   0.7661   0.0921
  -2.500   0.4788   0.00946   0.00295  -0.1719   0.7615   0.1002
  -2.250   0.5062   0.00927   0.00288  -0.1718   0.7560   0.1223
  -2.000   0.5340   0.00912   0.00282  -0.1717   0.7498   0.1587
  -1.750   0.5619   0.00906   0.00276  -0.1715   0.7431   0.1801
  -1.500   0.5890   0.00897   0.00271  -0.1712   0.7354   0.1968
  -0.750   0.6716   0.00881   0.00265  -0.1707   0.7150   0.2589
  -0.500   0.6990   0.00879   0.00267  -0.1705   0.7081   0.2836
  -0.250   0.7260   0.00876   0.00269  -0.1702   0.6998   0.3072
   0.000   0.7530   0.00877   0.00271  -0.1699   0.6915   0.3287
   0.250   0.7796   0.00877   0.00273  -0.1695   0.6815   0.3472
   0.500   0.8061   0.00878   0.00276  -0.1691   0.6711   0.3644
   0.750   0.8322   0.00881   0.00277  -0.1686   0.6592   0.3807
   1.000   0.8574   0.00884   0.00279  -0.1679   0.6435   0.3965
   1.250   0.8819   0.00891   0.00282  -0.1671   0.6221   0.4112
   1.500   0.9047   0.00903   0.00287  -0.1660   0.5973   0.4282
   1.750   0.9273   0.00919   0.00297  -0.1649   0.5743   0.4488
   2.000   0.9502   0.00937   0.00312  -0.1639   0.5564   0.4724
   2.250   0.9736   0.00953   0.00329  -0.1630   0.5426   0.5034
   2.500   0.9969   0.00971   0.00348  -0.1621   0.5310   0.5485
   2.750   1.0213   0.00981   0.00368  -0.1614   0.5209   0.6005
   3.000   1.0446   0.00989   0.00387  -0.1605   0.5121   0.6627
   3.250   1.0674   0.00949   0.00403  -0.1593   0.5039   1.0000
   3.500   1.0917   0.00973   0.00420  -0.1586   0.4965   1.0000
   3.750   1.1171   0.00990   0.00435  -0.1581   0.4896   1.0000
   4.000   1.1412   0.01014   0.00453  -0.1574   0.4828   1.0000
   4.250   1.1658   0.01033   0.00470  -0.1567   0.4761   1.0000
   4.500   1.1900   0.01052   0.00487  -0.1560   0.4692   1.0000
   4.750   1.2132   0.01078   0.00507  -0.1551   0.4630   1.0000
   5.000   1.2378   0.01093   0.00525  -0.1545   0.4566   1.0000
   5.250   1.2603   0.01116   0.00545  -0.1535   0.4493   1.0000
   5.500   1.2830   0.01136   0.00564  -0.1525   0.4416   1.0000
   5.750   1.3046   0.01158   0.00585  -0.1513   0.4338   1.0000
   6.000   1.3253   0.01181   0.00606  -0.1500   0.4266   1.0000
   6.250   1.3450   0.01203   0.00628  -0.1484   0.4175   1.0000
   6.500   1.3642   0.01228   0.00652  -0.1468   0.4087   1.0000
   6.750   1.3837   0.01254   0.00678  -0.1453   0.4007   1.0000
   7.000   1.4030   0.01281   0.00705  -0.1437   0.3924   1.0000
   7.250   1.4198   0.01316   0.00736  -0.1418   0.3812   1.0000
   7.500   1.4375   0.01349   0.00768  -0.1401   0.3682   1.0000
   7.750   1.4534   0.01390   0.00806  -0.1380   0.3530   1.0000
   8.000   1.4683   0.01438   0.00849  -0.1359   0.3364   1.0000
   8.250   1.4807   0.01499   0.00901  -0.1335   0.3164   1.0000
   8.500   1.4907   0.01575   0.00964  -0.1308   0.2877   1.0000
   8.750   1.4947   0.01687   0.01055  -0.1273   0.2486   1.0000
   9.000   1.4973   0.01816   0.01162  -0.1238   0.2143   1.0000
   9.250   1.5058   0.01917   0.01254  -0.1212   0.1994   1.0000
   9.500   1.5163   0.02009   0.01343  -0.1190   0.1903   1.0000
   9.750   1.5258   0.02109   0.01440  -0.1167   0.1827   1.0000
  10.000   1.5382   0.02194   0.01528  -0.1149   0.1771   1.0000
  10.250   1.5494   0.02289   0.01624  -0.1129   0.1715   1.0000
  10.500   1.5577   0.02405   0.01739  -0.1108   0.1659   1.0000
  10.750   1.5722   0.02483   0.01824  -0.1094   0.1611   1.0000
  11.000   1.5835   0.02585   0.01929  -0.1077   0.1556   1.0000
  11.250   1.5900   0.02724   0.02067  -0.1056   0.1494   1.0000
  11.500   1.6070   0.02791   0.02142  -0.1046   0.1431   1.0000
  11.750   1.6149   0.02926   0.02275  -0.1029   0.1350   1.0000
  12.000   1.6282   0.03024   0.02376  -0.1017   0.1231   1.0000
  12.250   1.6330   0.03192   0.02532  -0.0999   0.1015   1.0000
  12.500   1.6319   0.03415   0.02743  -0.0978   0.0868   1.0000
  12.750   1.6339   0.03622   0.02950  -0.0960   0.0804   1.0000
  13.000   1.6336   0.03856   0.03185  -0.0943   0.0752   1.0000
  13.250   1.6387   0.04048   0.03383  -0.0930   0.0721   1.0000
  13.500   1.6414   0.04270   0.03611  -0.0917   0.0691   1.0000
  13.750   1.6415   0.04524   0.03869  -0.0904   0.0662   1.0000
  14.000   1.6440   0.04762   0.04114  -0.0894   0.0638   1.0000
  14.250   1.6494   0.04975   0.04336  -0.0886   0.0617   1.0000
  14.500   1.6516   0.05229   0.04597  -0.0878   0.0592   1.0000
  14.750   1.6503   0.05531   0.04902  -0.0871   0.0568   1.0000
  15.000   1.6527   0.05798   0.05178  -0.0865   0.0545   1.0000
  15.250   1.6574   0.06042   0.05431  -0.0862   0.0520   1.0000
  15.500   1.6576   0.06350   0.05744  -0.0859   0.0494   1.0000
  15.750   1.6567   0.06682   0.06082  -0.0857   0.0468   1.0000
  16.000   1.6608   0.06953   0.06362  -0.0857   0.0435   1.0000
  16.250   1.6569   0.07340   0.06751  -0.0859   0.0406   1.0000
  16.500   1.6595   0.07644   0.07063  -0.0861   0.0367   1.0000
  16.750   1.6555   0.08049   0.07472  -0.0865   0.0337   1.0000
  17.000   1.6535   0.08431   0.07860  -0.0870   0.0307   1.0000
  17.250   1.6481   0.08869   0.08303  -0.0878   0.0285   1.0000
  17.500   1.6447   0.09281   0.08723  -0.0885   0.0267   1.0000
  17.750   1.6382   0.09749   0.09196  -0.0896   0.0252   1.0000
  18.000   1.6326   0.10208   0.09664  -0.0907   0.0241   1.0000
  18.250   1.6288   0.10641   0.10107  -0.0919   0.0231   1.0000
  18.500   1.6236   0.11097   0.10572  -0.0932   0.0222   1.0000
  18.750   1.6169   0.11585   0.11067  -0.0948   0.0215   1.0000
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